US6019717A - Nozzle inlet enhancement for a high speed turbine-driven centrifuge - Google Patents

Nozzle inlet enhancement for a high speed turbine-driven centrifuge Download PDF

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US6019717A
US6019717A US09/209,570 US20957098A US6019717A US 6019717 A US6019717 A US 6019717A US 20957098 A US20957098 A US 20957098A US 6019717 A US6019717 A US 6019717A
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Prior art keywords
cone
flow
passageway
turbine
rotor
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US09/209,570
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English (en)
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Peter K. Herman
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Cummins Filtration Inc
Cummins Filtration IP Inc
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Fleetguard Inc
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Priority claimed from US09/136,736 external-priority patent/US6017300A/en
Application filed by Fleetguard Inc filed Critical Fleetguard Inc
Assigned to FLEETGUARD, INC. reassignment FLEETGUARD, INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HERMAN, PETER K.
Priority to US09/209,570 priority Critical patent/US6019717A/en
Priority to AU63158/99A priority patent/AU760173B2/en
Priority to JP35100599A priority patent/JP3585795B2/ja
Priority to DE69906019T priority patent/DE69906019T2/de
Priority to EP99309967A priority patent/EP1008391B1/fr
Publication of US6019717A publication Critical patent/US6019717A/en
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Assigned to KUSS CORPORATION reassignment KUSS CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: FLEETGAURD, INC.
Assigned to CUMMINS FILTRATION IP,INC. reassignment CUMMINS FILTRATION IP,INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KUSS CORPORATION
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B04—CENTRIFUGAL APPARATUS OR MACHINES FOR CARRYING-OUT PHYSICAL OR CHEMICAL PROCESSES
    • B04B—CENTRIFUGES
    • B04B9/00—Drives specially designed for centrifuges; Arrangement or disposition of transmission gearing; Suspending or balancing rotary bowls
    • B04B9/06—Fluid drive
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B04—CENTRIFUGAL APPARATUS OR MACHINES FOR CARRYING-OUT PHYSICAL OR CHEMICAL PROCESSES
    • B04B—CENTRIFUGES
    • B04B1/00—Centrifuges with rotary bowls provided with solid jackets for separating predominantly liquid mixtures with or without solid particles
    • B04B1/04—Centrifuges with rotary bowls provided with solid jackets for separating predominantly liquid mixtures with or without solid particles with inserted separating walls
    • B04B1/08—Centrifuges with rotary bowls provided with solid jackets for separating predominantly liquid mixtures with or without solid particles with inserted separating walls of conical shape
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B04—CENTRIFUGAL APPARATUS OR MACHINES FOR CARRYING-OUT PHYSICAL OR CHEMICAL PROCESSES
    • B04B—CENTRIFUGES
    • B04B5/00—Other centrifuges
    • B04B5/005—Centrifugal separators or filters for fluid circulation systems, e.g. for lubricant oil circulation systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01M—LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING
    • F01M1/00—Pressure lubrication
    • F01M1/10—Lubricating systems characterised by the provision therein of lubricant venting or purifying means, e.g. of filters
    • F01M2001/1028—Lubricating systems characterised by the provision therein of lubricant venting or purifying means, e.g. of filters characterised by the type of purification
    • F01M2001/1035—Lubricating systems characterised by the provision therein of lubricant venting or purifying means, e.g. of filters characterised by the type of purification comprising centrifugal filters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01M—LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING
    • F01M13/00—Crankcase ventilating or breathing
    • F01M13/04—Crankcase ventilating or breathing having means for purifying air before leaving crankcase, e.g. removing oil
    • F01M2013/0422—Separating oil and gas with a centrifuge device

Definitions

  • the present invention relates generally to the continuous separation of solid particles, such as soot, from a fluid, such as oil, by the use of a centrifugal field. More particularly the present invention relates to the use of a cone (disk) stack centrifuge configuration within a centrifuge assembly which includes a turbine wheel for rotatably driving a rotor. The turbine wheel is driven by jet nozzles tangentially aligned with the runner circular centerline.
  • Diesel engines are designed with relatively sophisticated air and fuel filters (cleaners) in an effort to keep dirt and debris out of the engine. Even with these air and fuel cleaners, dirt and debris, including engine-generated wear debris, will find a way into the lubricating oil of the engine. The result is wear on critical engine components and if this condition is left unsolved or not remedied, engine failure. For this reason, many engines are designed with fill flow oil filters that continually clean the oil as it circulates between the lubricant sump and engine parts.
  • centrifuge cleaners can be configured in a variety of ways as represented by the earlier designs of others, one product which is representative of part of the early design evolution is the Spinner II® oil cleaning centrifuge made by Glacier Metal Company Ltd., of Somerset, Ilminister, United Kingdom, and offered by T. F. Hudgins, Incorporated, of Houston, Tex.
  • Various advances and improvements to the Spinner II® product are represented by U.S. Pat. No. 5,575,912 issued Nov. 19, 1996 to Herman and by U.S. Pat. No. 5,637,217 issued Jun. 10, 1997 to Herman and these two patents are expressly incorporated by reference herein for their entire disclosures.
  • centrifugal separators are typically driven at.
  • the typical or normal rotational speed for Hero- turbine centrifugal separators is in the range of approximately 5000 RPMs for a rotor with a 4.75 inch outside diameter cone stack and approximately 7000 RPMs for a rotor with a 3.50 inch outside diameter cone stack. These speeds are not fast enough to remove the soot at an adequate rate in order to control soot build up in the oil. Rates of approximately twice those listed are needed to effectively attack the soot build-up problem.
  • the oil in the sump begins as clean oil and, over time with operation of the engine, soot gradually builds up.
  • the objective is to control the percentage of soot in the sump oil. While an equilibrium condition will, in time, be established where the removal rate is the same as the add rate, the key is the percentage of soot.
  • the governing equation is the following: ##EQU1##
  • the removal efficiency and the flow rate are coupled such that just doubling the flow rate cuts the efficiency by one-half.
  • the key is the removal efficiency. If this can be increased, the soot concentration in the sump will be decreased without altering any other factors or components.
  • centrifugal separator In view of the discussed concerns and issues with regard to present centrifugal separator designs, it would be an improvement to devise a configuration suitable to generate a faster drive (rotational) speed. Testing has shown that by driving a centrifugal separator at a rotational speed closer to 10,000 RPMs, it is possible to demonstrate drastic soot reduction from an approximate 4.1 percent level to an approximate 0.8 percent level in the lubricant fluid in 280 hours of sump circulation (off-engine testing).
  • the present invention provides an improved structure for a cone-stack centrifugal separator which is capable of generating the desired 10,000 RPM speed without needing to increase the lube system pressure above the normal and desired operating pressure of 70 PSI.
  • the operating pressure range is from approximately 40 PSI to an upper limit of approximately 90 PSI.
  • bearings which support the rotor need to be designed to withstand and contain the pressure inside the rotor. While journal bearings are preferred for these elevated pressure levels, these bearings have a rotational drag coefficient, caused by viscous shear of thin oil film between bearing and shaft, which precludes the cone-stack centrifuge from being driven at the desired 10,000 RPM (or higher) speed. By reducing the operating pressure inside the centrifuge rotor, roller bearings are able to be used which have a substantially lower drag coefficient, allowing a higher speed of rotation.
  • a cone-stack centrifuge for separating particulate matter out of a circulating fluid comprises a cone-stack assembly including a hollow rotor hub and being designed to rotate about an axis, a base assembly which defines a liquid inlet, a first passageway, a second passageway connected to the first passageway and a hollow base hub, the liquid inlet being connected to the hollow base hub by the first shaft passageway, a shaft centertube attached to the base hub and extending through the rotor hub, a bearing positioned between the rotor hub and the shaft centertube for rotary motion of the cone-stack assembly, a turbine wheel attached to the rotor hub, and a flow jet nozzle flow coupled to the second passageway for directing a flow jet of liquid at the turbine wheel in order to drive the turbine wheel which in turn imparts rotary motion to the cone-stack assembly.
  • a related embodiment of the present invention includes the use of a honeycomb-like insert assembled into the inlet of the flow jet nozzle in
  • One object of the present invention is to provide an improved cone-stack centrifuge.
  • FIG. 1 is a front elevational view in full section of a cone-stack centrifuge according to a typical embodiment of the present invention.
  • FIG. 1A is a partial front elevational view in full section of a cone-stack centrifuge according to another embodiment of the present invention.
  • FIG. 2 is a diagrammatic top plan view of a impulse turbine and cooperating jet nozzles which comprise part of the FIG. 1 cone-stack centrifuge.
  • FIG. 2A is a front elevational view in full section of a modified half-bucket for use as part of the FIG. 2 impulse turbine which is used in the FIG. 1 cone-stack centrifuge.
  • FIG. 2B is a perspective view of the FIG. 2A modified half-bucket.
  • FIG. 3 is a front elevational view in full section of a center shaft which comprises one part of the FIG. 1 cone-stack centrifuge.
  • FIG. 4 is a front elevational view in full section of a rotor hub which comprises one part of the FIG. 1 cone-stack centrifuge.
  • FIG. 5 is a top plan view of the FIG. 4 rotor hub.
  • FIG. 6 is a front elevational view in full section of a cone-stack centrifuge according to an alternative embodiment of the present invention.
  • FIG. 6A is a partial, front elevational view in full section of a cone-stack centrifuge according to another embodiment of the present invention.
  • FIG. 7 is a front elevational view in full section of a center shaft which comprises one part of the FIG. 6 cone-stack centrifuge.
  • FIG. 8 is a front elevational view in full section of a base which comprises one part of the FIG. 6 cone-stack centrifuge.
  • FIG. 9 is a partial, front elevational view in full section of a vane-ring style of impulse turbine suitable for use as part of the cone-stack centrifuge according to the present invention.
  • FIG. 10 is a partial, top plan view of the FIG. 9 vane-ring style turbine.
  • FIG. 11 is a diagrammatic illustration of one vane of the FIG. 9 vane-ring style turbine and cooperating nozzle jet.
  • FIG. 12 is an end elevational view of a jet nozzle insert for use as part of the cone-stack centrifuge according to the present invention.
  • FIG. 13 is an end elevational view of an alternative jet nozzle insert for use as part of the cone-stack centrifuge according to the present invention.
  • FIG. 14 is a front elevational view in full section of a representative mounting post and jet nozzle incorporating the FIG. 12 jet nozzle insert.
  • Centrifuge 20 includes as some of its primary components base 21, bell housing 22, shaft 23, rotor hub 24, rotor 25, cone stack 26, jet nozzles 27 and 28, and modified Pelton turbine 29.
  • the rotor 25 includes a cone-stack assembly.
  • FIG. 2 provides a diagrammatic top plan view of jet nozzles 27 and 28 as well as impulse turbine 29 showing the direction of the flow jets 27a and 28a exiting from jet nozzles 27 and 28, respectively.
  • Turbine 29 includes a circumferential series of eighteen buckets 32 attached to a rotatable wheel 33.
  • the flow jets 27a and 28a are directed tangentially to the wheel on opposite sides of the wheel, and are aimed at the center of the buckets which rotate into the tangency zone on the corresponding side of wheel 33.
  • Rotatable wheel 33 is securely and rigidly attached to rotor hub 24 which is concentrically positioned around shaft 23.
  • the rotor hub is bearingly mounted to and supported by shaft 23 by means of upper roller bearing 34 and lower roller bearing 35. Sealed bearings are used as opposed to shielded bearings in order to reduce bearing leakage flow.
  • turbine 29 can be configured in a variety of styles
  • the preferred configuration for the present invention is a modified half-bucket style of Pelton turbine.
  • the modified half-bucket turbine 29 is illustrated in FIG. 1 while a conventional Pelton turbine 29a (split-bucket) is illustrated in FIG. 1A.
  • the differences between these two turbine options are effectively limited to the geometry of the buckets, 32 and 32a, respectively.
  • the construction of the FIG. 1 and FIG. 1A centrifuges are identical.
  • the construction of a split-bucket 32a is believed to be well known, the modified half-bucket 32 configuration is unique to this application. Reference to FIGS. 2A and 2B will provide additional details regarding the geometry and construction of each half-bucket 32.
  • the cone-stack assembly or rotor 25 is defined herein as including as its primary components base plate 38, vessel shell 39, and cone stack 26.
  • the assembly of these primary components is attached to rotor hub 24 such that as rotor hub 24 rotates around shaft 23 by means of roller bearings 34 and 35, the rotor 25 rotates.
  • the rotary motion imparted to rotor hub 24 comes from the action of turbine 29 which is driven by the high pressure flow out of jet nozzles 27 and 28.
  • each bucket 32 (the modified half-bucket style) has an ellipsoidal profile and a 10 to 15 degree exit angle on the edge of the ellipsoid.
  • a front elevational view of one bucket 32 is illustrated in FIG. 2A.
  • a perspective view of one bucket 32 is illustrated in FIG. 2B. The flow exiting from the bucket is directed downward and away from the spinning rotor, thus reducing droplet impingement drag.
  • centrifuge 20 is similar in certain respects to the structure disclosed in U.S. Pat. Nos. 5,575,912 and 5,637,217, which patents have been expressly incorporated by reference herein. More specifically, the outer radial lip 40 of the bell housing 22 is positioned on the upper surface of flange 41. The interface between radial lip 40 and flange 41 is sealed in part by the addition of an intermediate annular, rubber O-ring 42. A band clamp 45 is used to complete and complement the sealed interface. Clamp 45 is positioned around the lip 40 and flange 41 and includes an inner annular clamp 46 and an outer annular band 47.
  • a cap assembly 51 is provided for receipt and support of the externally-threaded end 52 of shaft 23.
  • the details of shaft 23 are illustrated in FIG. 3.
  • Adapter 53 is internally threaded and includes a flange 54 that fits through and up against the edge of opening 55.
  • Sleeve 56, O-ring 57, and cap 58 complete the assembly. With the end 52 first threaded into adapter 53, and with the O-ring assembled, the housing and sleeve are then lowered into position. The cap is attached to secure the cap assembly 51 to the shaft 23 and housing 22 and the band clamp assembled and tightened into position.
  • Cap assembly 51 provides axial centering for the upper end 52 of shaft 23 and for the support and stabilizing of shaft 23 in order to enable smooth and high speed rotation of rotor 25.
  • an attachment nut 61 and support washer 62 Disposed at the upper end of the rotor 25, between the bell housing 22 and the externally-threaded end 52, is an attachment nut 61 and support washer 62.
  • the annular support washer has a contoured shaped which corresponds to the shape of the upper portion of rotor shell 39.
  • An alternative envisioned for the present invention in lieu of a separate component for washer 62 is to integrate the support washer function into the rotor shell by fabricating an impact extruded shell with a thick section at the washer location.
  • Upper end 63 of rotor hub 24 is bearingly supported by shaft 23 and upper bearing 34 and is externally threaded. Attachment nut 61 is threadedly tightened onto upper end 63 and this draws the support washer 62 and rotor shell 39 together.
  • the opposite (lower) end 64 of rotor hub 24 is configured with a series of axial notches 64a and an alternating series of outwardly extending splines 64b (see FIGS. 4 and 5).
  • This splined end fits tightly within the cylindrical aperture 65 which is centered in base plate 38.
  • Aperture 65 is concentric with hub 24 and with shaft 23 and the anchoring of the hub to the housing and to the base plate ensures a concentric rotation of the cone-stack assembly around the shaft 23.
  • the fit between the splined end 64 and aperture 65 also creates a series of spaced-apart, exiting flow channels 66 by way of the notches 64a and splines 64b.
  • a radial seal is established between the inner surface 67 of lower edge 68 of rotor shell 39 and the outer annular surface 69 of base plate 38.
  • This sealed interface is determined in part by the closeness of the fit and in part by the use of annular, rubber O-ring 70.
  • O-ring 70 is compressed between the inner surface 67 and the outer annular surface 69.
  • the assembly between the rotor shell 39 and base plate 38 in combination with O-ring 70 creates a sealed enclosure defining an interior volume 73 which contains cone stack 26.
  • Each cone 74 of the cone stack 26 has a center opening 75 and a plurality of inlet holes disposed around the circumference of the cone adjacent the outer annular edge 77.
  • Typical cones for this application are illustrated and disclosed in U.S. Pat. Nos. 5,575,912 and 5,637,217.
  • the typical flow path for the rotor 25 begins with the flow of liquid upwardly through the hollow center 78 of rotor hub 24. The flow through the interior of the rotor hub exits out through apertures 79. A total of eight equally-spaced apertures 79 are provided, see FIG. 4.
  • a flow distribution plate 80 is configured with vanes and used to distribute the exiting flow out of hub 24 across the surface of the top cone 74a.
  • the manner in which the liquid (lubricating oil) flows across and through the individual cones 74 of the cone stack 26 is a flow path and flow phenomenon which is well known in the art.
  • This flow path and the high RPM spinning rate of the cone-stack assembly enables the small particles of soot which are carried by the oil to be centrifugally separated out of the oil and held in the centrifuge.
  • the focus of the present invention is on the design of base 21, the use of a turbine 29, the manner of routing a fluid to the flow jet nozzles 27 and 28, and the configuration of shaft 23 which provides the desired design compatibility with the base 21, turbine 29, and nozzles 27 and 28.
  • the base 21 is configured with and defines an inlet aperture 82 and main passageway 83. Intersecting main passageway 83 at right angles are jet nozzle passageways 84 and 85.
  • Passageway 84 is defined by mounting post 86 and provides a fluid communication path to jet nozzle 27.
  • On the opposite side of wheel 33 and on the opposite side of base hub 87 for mounting post 86 is a second mounting post 88 which defines passageway 85.
  • Passageway 85 provides a fluid communication path to jet nozzle 28.
  • the hub 87 of base 21 includes a cylindrical aperture 89 which is internally threaded and which intersects main passageway 83 at a right angle.
  • the base 90 of shaft 23 is externally threaded and threadedly secured and assembled into aperture 89.
  • Base 90 is hollow and defines passageway 91, which has a blind distal end 92 and throttle passageway 93.
  • the distal end of passageway 83 is closed (i.e., blind) as is the distal end of passageway 84 and the distal end of passageway 85.
  • splined end 64 of rotor hub 24 into cylindrical aperture 65 supports the rotor hub 24 within base plate 38 and maintains the securely assembled status between base plate 38, rotor shell 39, and rotor hub 24.
  • a press fit or even a tight fit between end 64 and aperture 65 is sufficient for the desired support.
  • the splined fit between end 64 and aperture 65 is also designed to prevent relative rotational movement between the rotor hub 24 and base plate 38.
  • the fit of end 64 within aperture 65 creates exiting flow channels 66 which open into the interior space 95 of base 21 defined by the side wall 96 of base 21.
  • Side wall 96 further defines outlet drain opening 97 which permits the oil exiting from the rotor 25 by way of flow channel 66 to drain out from base 21 and continue on its circulatory path to and through the corresponding engine, or other item of equipment.
  • the lubricating oil which is used through the jet nozzles 27 and 28 to drive the turbine 29 also accumulates in interior space 95 and combines with the oil exiting through flow channel 66 and it is this blended oil which exits through the outlet drain opening 97.
  • Splash plate 98 is attached to the upper end surface 99 and 100 of posts 86 and 88, respectively.
  • pressurized (20-90 PSI) fluid flow enters the centrifuge base 21 via inlet aperture 82 and main passageway 83.
  • Pressurized oil is supplied to passageways 84 and 85 as well as to passageway 91 by way of cylindrical aperture 89.
  • Post 86 defines an exit orifice 103 which flow connects with jet nozzle 27.
  • a similar exit orifice 104 is defined by post 88 and flow connects with jet nozzle 28.
  • the blind nature of passageways 84 and 85 forces the entering flow out through orifices 103 and 104 in order to create flow jets 27a and 28a which drive the turbine 29 which in turn rotatably drives rotor hub 24 and the remainder of rotor 25.
  • the high velocity streams of fluid exiting from the two flow jet nozzles create the necessary high RPM speed for the rotor 25 in order to achieve the desired soot removal rate from the oil being routed through the rotor 25.
  • the requisite speed is a function of the outside diameter size of the cone stack as previously discussed.
  • jet nozzles 27 and 28 each have an exit orifice sized at a diameter of approximately 2.46 mm (0.09 inches). Each nozzle has a tapered design on the interior so as to create a smooth transition leading to the exit orifice diameter in order to develop a coherent stable jet with minimal turbulent energy and maximum possible velocity.
  • the turbine 29 converts the kinetic energy of the jets to torque which is imparted to the rotor hub 24. As has been described, various styles or designs for turbine 29 are contemplated within the scope and teachings of the present invention, including a classic Pelton turbine, though miniaturized in size, a modified half-bucket style, and a vane-ring or "turgo" style.
  • the modified half-bucket style is the preferred choice.
  • the turbine is optimized in performance efficiency when the bucket velocity is slightly less than one-half that of the impinging flow jet velocity.
  • the driving fluid "drops off" the bucket with nearly zero residual velocity and falls down into the interior space 95 of the base and exits by way of drain opening 97.
  • a target speed of 10,000 RPMs with a 70 PSI jet, a design for turbine 29 with a bucket pitch diameter of 28.96 mm (1.14 inches), and a delivery torque of approximately 1 inch/pound are characteristics of the design of the preferred embodiment. Under these specifications, the pumping horsepower (parasitic) loss to the engine is only 0.2 HP (less than 0.03 percent of engine output for the size of engine under study for these conditions).
  • the entering oil by way of passageway 83 also flows up through cylindrical aperture 89 into passageway 91 of shaft 23.
  • the upward flow exits the interior of shaft 23 by way of throttle passageway 93.
  • the exit orifice diameter for passageway 93 is 1.85 mm (0.073 inches) which limits the flow rate through the rotor 25 to approximately 0.6 gallons per minute.
  • a flow of 0.6 gallons per minute avoids this problem.
  • a critical aspect of the present invention is the throttling of the incoming flow by the use of passageway 93 which is located adjacent to the inlet end 107 of the rotor hub 24.
  • the rotor hub 24 extends in an upward direction from base 21 and base plate 38 to the area of the attachment nut 61 at the upper end or top of the vessel shell 39. Since the incoming oil enters at aperture 82 and from there flows in and up, the lower end 107 of the rotor hub is the inlet end for the purpose of defining the flow path.
  • the use of these styles of roller bearings dramatically reduces the rotational drag compared to the prior art (old style) journal bearings.
  • journal bearings are needed since they can withstand the higher pressure.
  • the problem is that journal bearings have substantial levels of rotational drag which limit the RPM speed which can be achieved for the rotor 25.
  • the process fluid travels upwardly in the hollow center or interior 78 of rotor hub 24 between the shaft 23 and hub 24.
  • the process fluid travels upwardly in the hollow center or interior 78 of rotor hub 24 between the shaft 23 and hub 24.
  • the flowing oil passes through each of these outlet holes 79 and the flow is directed up and around the cone stack by a flow distribution plate which is equipped with radial vanes that accelerate the fluid in the tangential direction.
  • the flow is distributed throughout the cone stack through the vertically-aligned cone inlet holes and flows through the gaps in the cone stack radially inwards toward the hub.
  • the stack of cones is rigidly supported by the rotor hub base plate. Upon reaching the hub outside diameter, the flow passes down through aligned cut outs on the inside diameter of the cones and exits the interior volume 73 through the flow channels 66.
  • the base plate 38 can be a one-piece design with holes drilled through the plate for fluid exit paths.
  • the splash plate is not used, then the exiting oil needs to exit from a point lower than the lowest point of the base plate so that oil is not re-entrained on the surface of the spinning rotor as it flies radially outward from the exit point.
  • the "clean" process fluid then mixes with the driving fluid and drains out of the housing base 21 by way of drain opening 97 through the force of gravity.
  • centrifuge 120 has a structure which in many respects is quite similar to the cone-stack centrifuge 20 of FIG. 1.
  • the principal differences between cone stack centrifuge 120 and cone-stack centrifuge 20 involve the designs and the relationships for the base 21, shaft 23, cylindrical aperture 89, and main passageway 83. Comparing these portions of centrifuge 20 with the corresponding portions of centrifuge 120 reveals the following differences.
  • the main passageway 83 is in direct flow communication with aperture 89 of base hub 87.
  • the aperture 89 does not axially extend through the main passageway 83, but effectively is a T-intersection at that point.
  • FIG. 1 design for centrifuge 20
  • the main passageway 83 is in direct flow communication with aperture 89 of base hub 87.
  • the aperture 89 does not axially extend through the main passageway 83, but effectively is a T-intersection at that point.
  • the base 123 of shaft 124 still includes a passageway 127 which provides a flow path from inlet aperture 128 to throttle passageways 129 and 130.
  • Turbine 29 is now numbered as 134, but the designs are basically the same.
  • FIG. 6A the alternative style of turbine with the split-bucket configuration is identified as turbine 134a.
  • shaft 23 includes a single throttle passageway 93 while shaft 124 (FIG. 6) includes two throttle passageways, 129 and 130.
  • shaft 124 FIG. 6
  • the incoming oil is also used to drive the turbine 29 and throttling the flow outside of the centrifuge would adversely affect the turbine speed.
  • throttling of the flow to the rotor 25 is accomplished by passageway 93. It is easier to accomplish the throttling function with one passageway as compared to two. For this reason, only a single passageway 93 is provided in the FIG. 1 embodiment.
  • Turbine 134 is virtually identical to turbine 29 and the balance of centrifuge 120 is virtually identical to centrifuge 20, except as being described herein.
  • a pressurized fluid is introduced into main passageway 122 by way of inlet aperture 137.
  • this pressurized fluid i.e., driving fluid
  • the pressurized gas follows the same path as the oil in the FIG. 1 configuration except that the pressurized gas does not flow into passageway 127 and, as such, is not introduced into the cone-stack assembly 138.
  • the base 123 of shaft 124 is notched or indented at location 141 in order to permit the pressurized gas a free flow path around the base 123 of shaft 124.
  • Passageway 142 in post 143 is in communication with passageway 122 for the delivery of the pressurized gas to jet nozzle 135.
  • An O-ring 144 is positioned between base 123 and the lower aperture extension 125.
  • Inlet aperture 128 is internally threaded for coupling the input conduit which delivers the fluid to be introduced into the cone-stack assembly.
  • the gas typically air which is used to drive the turbine 134 in FIG. 6 must be vented from the centrifuge 120 to the atmosphere. While a variety of vent designs and locations are suitable for this function, it is important to first separate any oil mist which may have co-mingled with the air.
  • a coalescer 150 is attached to bell housing 151 and sealed around outlet 152. As the spray mist or aerosol of air and oil exits through outlet 152, the interior of the coalescer 150 pulls the oil out of the air. The air then passes to the atmosphere and the oil gradually drips back into the centrifuge.
  • the interior of coalescer 150 includes a metal mesh or alternatively a woven or non- woven synthetic mesh, all of which are well known in the art.
  • FIG. 1A Various styles or designs for turbine 29 and the corresponding buckets have been mentioned herein, including a classic Pelton turbine 29a with its split-bucket configuration for the individual buckets 32a (FIG. 1A) and a modified half-bucket style of turbine 29 with its buckets 32 (FIG. 1).
  • Either style of impulse turbine is suitable for the FIG. 1 and FIG. 6 embodiments as well as for the alternative embodiments of FIGS. 1A and 6A.
  • the diagrammatic illustration of FIG. 2 is intended to be a suitable generic representation of turbines 29 and 29a, even though numbered as turbine 29.
  • vane-ring or turgo style of turbine While the individual vanes of such a turbine style can be placed at virtually any diameter, the efficiency with the gas-driven mode of operation is improved if the vane circle diameter is increased over the illustrated bucket circle diameter for turbine 29.
  • the vane-ring style of turbine is preferred for gas-driven centrifuges. It is known that the optimal vane velocity is equal to one-half of the jet velocity and, based on choked flow (sonic velocity jet), it is preferable to locate the gas- driven vanes around a larger diameter.
  • FIGS. 9-11 illustrate a vane-ring turbine 160 which is created by the attachment of individual vanes 161 to the outer surface of the generally cylindrical portion 162a of the rotor shell 162 which is adjacent the lower edge 163.
  • Each vane 161 has a curved form with a concave impingement surface 164.
  • the jet nozzle 165 is directed at an angle of between 5 and 20 degrees relative to the vane centerline, an angle which generally coincides with the leading edge angle of the vane 61.
  • the jet nozzle 165 delivers a jet of air from passageway 166 which strikes the vanes in rotary sequence and thus drives (rotates) the rotor which is bearingly mounted onto the shaft.
  • the gas jet is at sonic velocity (for pressures above approximately 13 psig).
  • the optimal vane velocity (FIG. 9) for maximum kinetic energy extraction is about 0.4 times the jet velocity, which would be about 440 feet per second (for a sonic velocity of 1100 feet per second).
  • the vane velocity is approximately 320 feet per second which is still "slow" relative to optimal.
  • the vane (vane-ring) style of turbine used for the FIG. 9 centrifuge can be used with the centrifuge embodiments of FIGS. 1, 1A, 6, and 6A as a replacement for the modified half-bucket and split-bucket turbine styles. There are though efficiency differences based on the turbine style which is used, the location of the turbine, the rotor diameter, the driving medium, and the jet velocity.
  • the stationary jet nozzles 27 and 28 of FIG. 1 and the stationary jet nozzles 135 and 136 of FIG. 6 are modified by positioning a honeycomb-like insert 170 (see FIG. 12) in the inlet of each jet nozzle.
  • Each of the individual flow apertures 170a is defined by a hexagonally-shaped outer wall and extends the entire length of insert 170.
  • the function of insert 170 is to straighten the flow by removing or lessening the inlet turbulence.
  • This honeycomb-like insert 170 may also be used in conjunction with jet nozzle 165, if inlet turbulence is a concern.
  • FIGS. 1 and 6 the corresponding stationary jet nozzles 27 and 28 and 135 and 136, respectively, are positioned and assembled to corresponding mounting posts (86, 88, 140, and 143). Each mounting post defines an interior flow passageway which communicates with the inlet of its corresponding jet nozzle.
  • FIG. 14 provides a generic illustration of a representative jet nozzle and mounting post assembly for the purpose of describing the inlet turbulence and the positioning and functioning of insert 170.
  • the central flow axis 171 of representative jet nozzle 172 is generally perpendicular to the central flow axis 173 of flow passageway 174 in mounting post 175.
  • the flow from passageway 174 to nozzle inlet 176 necessitates a right angle turn. Whatever turbulence this might create is compounded by the nature of the closed end 177 of mounting post 175 and any reverse flow coming back toward inlet 176.
  • thermodynamic efficiency 50 to 60 percent can drop to as low as 25 to 35 percent due to the break up of the exiting flow stream.
  • honeycomb-like insert 170 By means of the honeycomb-like insert 170 there is an improvement in the turbine efficiency due to the improved coherency and stability of the liquid jet which is directed at the turbine buckets.
  • the insert 170 redirects the flow at inlet 176 so as to straighten it in the direction of the tapered outlet 178 of jet nozzle 172. This in turn creates more laminar entrance conditions at the nozzle throat, resulting in a coherent, stable exiting jet.
  • This improvement results in a substantial turbine efficiency gain which allows the centrifuge to achieve the desired speed with lower power consumption and lube-oil pumping.
  • Insert 170 is fabricated from a relatively thin section of aluminum foil having a thickness of approximately 8.9 mm (0.35 inches). Each individual cell 170a (hexagonal aperture) measures approximately 1.09 mm (0.043 inches) across opposite flat sides. The length of insert 170 is such that it is fully inserted into nozzle 172 up to the location of the throat where the inlet opening begins to taper. The opposite end of the insert 170 extends beyond the end of nozzle 172 into the interior of passageway 174 as illustrated in FIG. 14. The outside diameter size of surface 170b of insert 170 measures approximately 6.35 mm (0.25 inches) and is sized to fit closely in the jet nozzle inlet 176.
  • insert 170 includes the use of a molded plastic (see FIG. 13) or a die-cast metal such as Zn, Mg, or Al. These alternative materials would still produce an insert 170c with the described long and narrow capillary tube-like (cylindrical) passages 170d in order to create the desired laminar flow. Each passage 170d measures approximately 0.86 mm (0.034 inches) in diameter.

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  • Centrifugal Separators (AREA)
US09/209,570 1998-08-19 1998-12-11 Nozzle inlet enhancement for a high speed turbine-driven centrifuge Expired - Lifetime US6019717A (en)

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US09/209,570 US6019717A (en) 1998-08-19 1998-12-11 Nozzle inlet enhancement for a high speed turbine-driven centrifuge
AU63158/99A AU760173B2 (en) 1998-12-11 1999-12-06 Nozzle inlet enhancement for a high speed turbine-driven centrifuge
EP99309967A EP1008391B1 (fr) 1998-12-11 1999-12-10 Centrifugeuse à cônes empilés
DE69906019T DE69906019T2 (de) 1998-12-11 1999-12-10 Zentrifuge mit konischen Trennwänden
JP35100599A JP3585795B2 (ja) 1998-12-11 1999-12-10 遠心分離機

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US09/136,736 US6017300A (en) 1998-08-19 1998-08-19 High performance soot removing centrifuge with impulse turbine
US09/209,570 US6019717A (en) 1998-08-19 1998-12-11 Nozzle inlet enhancement for a high speed turbine-driven centrifuge

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US09/136,736 Continuation-In-Part US6017300A (en) 1998-08-19 1998-08-19 High performance soot removing centrifuge with impulse turbine

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US6354987B1 (en) * 1998-04-16 2002-03-12 Filterwerk Mann & Hummel Gmbh Free jet centrifuge
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US6517475B1 (en) 1998-09-25 2003-02-11 Baldwin Filters, Inc. Centrifugal filter for removing soot from engine oil
US6520902B1 (en) 1998-10-21 2003-02-18 Baldwin Filters, Inc. Centrifuge cartridge for removing soot from engine oil
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AU6315899A (en) 2000-06-15
JP2000176315A (ja) 2000-06-27
DE69906019T2 (de) 2003-08-21
EP1008391A3 (fr) 2001-09-12
EP1008391B1 (fr) 2003-03-19
EP1008391A2 (fr) 2000-06-14
AU760173B2 (en) 2003-05-08
JP3585795B2 (ja) 2004-11-04

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